CN218630564U - Power generation power supply controller of aero-generator - Google Patents

Power generation power supply controller of aero-generator Download PDF

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CN218630564U
CN218630564U CN202223062293.5U CN202223062293U CN218630564U CN 218630564 U CN218630564 U CN 218630564U CN 202223062293 U CN202223062293 U CN 202223062293U CN 218630564 U CN218630564 U CN 218630564U
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control unit
isolation
output
voltage
unit
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李游
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Shanxi Comet Intelligent Technology Co ltd
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Shanxi Comet Intelligent Technology Co ltd
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Abstract

The utility model relates to the technical field of high-power rectification power supply circuits, in particular to a power generation power supply controller of an aircraft generator; the aviation generator is connected with a rectifier bridge, the rectifier bridge is connected with a regulating unit, and the regulating unit is connected with external load equipment; the main control unit is connected with the isolation control unit, and the isolation control unit is connected with the adjusting unit; the rectifier bridge rectifies alternating current output by the aviation generator into first direct current, and then performs voltage stabilization and constant current output by the regulating unit to obtain second direct current; the output feedback circuits are respectively used for detecting the voltage and the current of the second direct current output by the regulating unit and feeding back the voltage and the current to the main control unit; the main control unit controls the regulating unit to regulate voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the regulating unit; the method comprises the steps of presetting a regulated voltage value and a constant current value of a second direct current to a main control unit; therefore, voltage stabilization and constant current output are realized, and the load equipment on the airplane has stable operation and low fault.

Description

Power generation power supply controller of aero-generator
Technical Field
The utility model relates to a high-power rectification power supply circuit technical field, more specifically say, relate to an aerogenerator's generating electrical source controller.
Background
Most of the current rectifier controllers of different permanent magnet generators can not carry out voltage stabilization output, and the defects of large circuit size, low output power and the like exist, so that the use requirements of people can not be met.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model lies in, to the above-mentioned defect of prior art, provide one kind and can carry out steady voltage output, circuit structure is succinct, small aero-generator's power generation controller.
The utility model provides a technical scheme that its technical problem adopted is:
constructing a power generation controller for an aircraft generator comprising: the device comprises a main control unit, an isolation control unit and an adjusting unit; the aircraft generator is connected with a rectifier bridge, the rectifier bridge is connected with the adjusting unit, and the adjusting unit is connected with external load equipment;
the rectifier bridge rectifies alternating current output by the aviation generator into first direct current, and then performs voltage stabilization and constant current output by the adjusting unit to obtain second direct current;
the main control unit is connected with the isolation control unit, and the isolation control unit is connected with the adjusting unit; the main control unit is also connected with a plurality of output feedback circuits, and the output feedback circuits are respectively used for detecting the voltage and the current of the second direct current output by the regulating unit and feeding the voltage and the current back to the main control unit;
the main control unit controls the adjusting unit to regulate voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the adjusting unit;
further comprising: and presetting the stabilized voltage value and the constant current value of the second direct current to the main control unit.
Aeronautical generator's generating electrical source controller, wherein, isolation control unit includes: the MOS tube isolation control units are connected with the adjusting unit;
the MOS tube isolation control unit comprises: the MOS transistor isolation control unit comprises a first gate drive chip, AN isolation power supply module and a second gate drive chip, wherein AN end AN of the first gate drive chip is a control signal input end of the MOS transistor isolation control unit, AN end CAT of the first gate drive chip is grounded, AN end VDD of the first gate drive chip is connected with AN end VO + of the isolation power supply module, AN end GND of the first gate drive chip is connected with AN end VO-of the isolation power supply module, AN end VOUT of the first gate drive chip is connected with AN end IN of the second gate drive chip and is also connected with a first resistor, and the other end of the first resistor is connected with AN end V of the isolation power supply module;
the VCC1 end and VCC2 end of the second grid drive chip are both connected with the VO + end of the isolation power module, the GND1 end and GND2 end of the second grid drive chip are both connected with the VO-end of the isolation power module, the OUT1 end and OUT2 end of the second grid drive chip are connected and are also connected with a second resistor, the other end of the second resistor is a drive signal output end of the MOS tube isolation control unit, the other end of the second resistor is also connected with a third resistor, and the other end of the third resistor is connected with the GND end of the isolation power module;
the GND end of the isolation power supply module is a driving signal return input end of the MOS tube isolation control unit;
and the driving signal output end and the driving signal return input end of the MOS tube isolation control unit are both connected with the adjusting unit.
Aerogenerator's generating electricity supply controller, wherein, it is a plurality of MOS manages isolation control unit and includes: the MOS tube isolation control unit is arranged on the upper tube, and the MOS tube isolation control unit is arranged on the lower tube; the adjusting unit comprises a plurality of SIC MOSFET modules, and a plurality of MOS tube isolation control units are connected with the SIC MOSFET modules;
the driving signal output end of the MOS tube isolation control unit of the upper tube is connected with 4 pins of the SIC MOSFET module, and the driving signal return input end is connected with 1 pin of the SIC MOSFET module;
the driving signal output end of the MOS tube isolation control unit for tube descending is connected with 6 pins of the SIC MOSFET module, and the driving signal return input end is connected with 2 pins of the SIC MOSFET module;
the 3 pins of the SIC MOSFET module are connected with the anode output end of the rectifier bridge, and the 2 pins of the SIC MOSFET module are connected with the cathode output end of the rectifier bridge;
and a pin 1 of the SIC MOSFET module is an anode output end of the second direct current and a pin 2 of the SIC MOSFET module is a cathode output end of the second direct current.
Aerogenerator's generating power supply controller, wherein, a plurality of MOS pipe isolation control unit and a plurality of SIC MOSFET module is connected one to one.
Aircraft generator's power generation electrical source controller, wherein, the main control unit is connected with level conversion unit, the main control unit includes: the level conversion unit comprises a plurality of third gate drivers, and the third gate drivers are respectively connected with the microcontroller and the MOS tube isolation control unit;
the INA end and the INB end of the third gate driver are connected with the RB15 end and the RB16 end of the microcontroller in a one-to-one mode, and the OUTA end and the OUTB end of the third gate driver are both connected with the MOS tube isolation control unit;
the OUTA end of the third grid driver is connected with the upper tube and the control signal input end of the MOS tube isolation control unit, and the OUTB end of the third grid driver is connected with the lower tube and the control signal input end of the MOS tube isolation control unit.
Aeronautical generator's generating power supply controller, wherein, the third grid driver still with a plurality of MOS manages the isolation control unit connection.
The utility model discloses a power generation controller of an aircraft generator, wherein, the output feedback circuit comprises an isolation transmitter and a shunt or a divider resistance unit;
the Sin-end and the Sin + end of the isolation transmitter are in one-to-one connection with the first detection output end and the second detection output end of the shunt or in one-to-one connection with the first detection output end and the second detection output end of the divider resistance unit;
and the Sout + end of the isolation transmitter is connected with the AN2 end or the AN3 end of the microcontroller, and the Sout-end is grounded.
The utility model discloses a power generation source controller of aerogenerator, wherein, a plurality of output feedback circuit include electric current output feedback circuit and voltage output feedback circuit;
the isolation transmitter and the current divider form the current output feedback circuit, and the isolation transmitter and the voltage dividing resistance unit form the voltage output feedback circuit;
the shunt is connected between the regulating unit and the anode of the load device in series, and the voltage dividing resistance unit is connected to the anode and the cathode of the second direct current in parallel.
Aerogenerator's generating electricity source controller, wherein, the first input of first potentiometre and second potentiometre all with reference power's positive pole be connected and the second input with reference power's negative pole is connected and ground connection, the output of first potentiometre with microcontroller's AN0 end is connected, the output of second potentiometre with microcontroller's AN1 end is connected.
The utility model discloses a power generation controller of aerogenerator, wherein, microcontroller supports the analog input; the first grid driving chip is of an isolation type.
The beneficial effects of the utility model reside in that: the rectifier bridge rectifies alternating current output by the aviation generator into first direct current, and then performs voltage stabilization and constant current output by the regulating unit to obtain second direct current; the output feedback circuits are respectively used for detecting the voltage and the current of the second direct current output by the regulating unit and feeding back the voltage and the current to the main control unit; the main control unit controls the regulating unit to regulate voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the regulating unit; the method comprises the steps of presetting a regulated voltage value and a constant current value of a second direct current to a main control unit; therefore, voltage-stabilizing constant-current output is realized, the operation of load equipment on the airplane is stable, the fault is low, the circuit structure is simple, and the size is small.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention will be further described with reference to the accompanying drawings and embodiments, wherein the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained without inventive efforts according to these drawings:
fig. 1 is a schematic circuit diagram of a MOS transistor isolation control unit of a power generation controller of an aircraft generator according to a preferred embodiment of the present invention;
fig. 2 is a schematic circuit diagram of a regulating unit of a power generation controller of an aircraft generator according to a preferred embodiment of the present invention;
fig. 3 is a schematic circuit diagram of a main control unit of a power generation controller of an aircraft generator according to a preferred embodiment of the present invention;
fig. 4 is a schematic circuit diagram of a level conversion unit of a power generation controller of an aircraft generator according to a preferred embodiment of the present invention;
fig. 5 is a schematic circuit diagram of an output feedback circuit of a power generation controller of an aircraft generator according to a preferred embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the following description will be made clearly and completely in conjunction with the technical solutions in the embodiments of the present invention, and obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
The power generation controller of the aero-generator according to the preferred embodiment of the present invention is shown in fig. 1, and also refer to fig. 2 to 5; the method comprises the following steps: a main control unit 300 and an isolation control unit (as shown in fig. 1) and a regulation unit 200; wherein, the aero-generator (not shown in the figure) is connected with a rectifier bridge (not shown in the figure), the rectifier bridge (not shown in the figure) is connected with the regulating unit 200, and the regulating unit 200 is connected with external load equipment;
the rectifier bridge rectifies alternating current output by the aircraft generator into first direct current, and then performs voltage stabilization and constant current output by the regulating unit 200 to obtain second direct current;
the main control unit 300 is connected with the isolation control unit, and the isolation control unit is connected with the adjusting unit 200; the main control unit 300 is further connected to a plurality of output feedback circuits 500, and the plurality of output feedback circuits 500 are respectively used for detecting the voltage and current of the second direct current output by the adjusting unit 200 and feeding back the voltage and current to the main control unit 300;
the main control unit 300 controls the adjusting unit 200 to adjust voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the adjusting unit 200;
further comprising: presetting a regulated voltage value and a constant current value of a second direct current to the main control unit 300;
the rectifier bridge rectifies alternating current output by the aircraft generator into first direct current, and then performs voltage stabilization and constant current output by the regulating unit 200 to obtain second direct current; the plurality of output feedback circuits 500 are respectively used for detecting the voltage and the current of the second direct current output by the regulating unit 200 and feeding back the voltage and the current to the main control unit 300; the main control unit 300 controls the adjusting unit 200 to regulate voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the adjusting unit 200; presetting a regulated voltage value and a constant current value of a second direct current to the main control unit 300; therefore, the voltage-stabilizing constant-current output is realized, the operation stability and the fault of load equipment on the airplane are low, and the circuit structure is simple and small.
As shown in fig. 1 and 2, the isolation control unit includes: the MOS transistor isolation control units 100 are connected with the adjusting unit 200;
the MOS transistor isolation control unit 100 includes: the transistor isolation control unit comprises a first gate drive chip U1, AN isolation power module DC1 and a second gate drive chip 1B, wherein the AN end of the first gate drive chip U1 is a control signal input end of the MOS transistor isolation control unit 100, the CAT end of the first gate drive chip U1 is grounded, the VDD end of the first gate drive chip U1 is connected with the VO + end of the isolation power module DC1, the GND end of the first gate drive chip U1 is connected with the VO-end of the isolation power module DC1, the VOUT end of the first gate drive chip U1 is connected with the IN end of the second gate drive chip 1B and is also connected with a first resistor R4, and the other end of the first resistor R4 is connected with the V-end of the isolation power module DC 1;
the VCC1 end and the VCC2 end of the second gate driving chip 1B are both connected with the VO + end of the isolation power module DC1, the GND1 end and the GND2 end are both connected with the VO-end of the isolation power module DC1, the OUT1 end and the OUT2 end of the second gate driving chip 1B are connected and are also connected with a second resistor R9, the other end of the second resistor R9 is a driving signal output end of the MOS transistor isolation control unit 100, the other end of the second resistor R9 is also connected with a third resistor R5, and the other end of the third resistor R5 is connected with the GND end of the isolation power module DC 1;
the GND end of the isolation power supply module DC1 is a driving signal return input end of the MOS tube isolation control unit 100;
the driving signal output end and the driving signal return input end of the MOS transistor isolation control unit 100 are both connected to the adjusting unit 200; the requirements of driving and controlling the SIC MOSFET module IGBT1 are met; the first gate driving chip U1 and the isolation power module DC1 are matched with the SIC MOSFET module IGBT1 for isolation, and the circuit stability is improved.
As shown in fig. 1 and 2, the plurality of MOS transistor isolation control units 100 includes: an upper tube MOS tube isolation control unit 100 and a lower tube MOS tube isolation control unit 100; the adjusting unit 200 comprises a plurality of SIC MOSFET modules (silicon carbide power modules) IGBT1, and the plurality of MOS tube isolation control units 100 are connected with the SIC MOSFET modules IGBT 1; the IGBT power module can be used for replacing the SIC MOSFET module, so that the cost is low, and different use requirements are met;
the output end of a driving signal of the upper tube MOS tube isolation control unit 100 is connected with 4 pins of an SIC MOSFET module IGBT1, and the input end of a driving signal return is connected with 1 pin of the SIC MOSFET module IGBT 1;
the output end of a driving signal of the lower tube MOS tube isolation control unit 100 is connected with 6 pins of an SIC MOSFET module IGBT1, and the input end of a driving signal return is connected with 2 pins of the SIC MOSFET module IGBT 1; namely, the upper MOS transistor isolation control unit 100 and the lower MOS transistor isolation control unit 100 cooperate to control the upper MOS transistor Q1 and the lower MOS transistor Q2 of the SIC MOSFET module IGBT1 in the adjusting unit 200;
the 3 pins of the SIC MOSFET module IGBT1 are connected with the anode output end of the rectifier bridge and the 2 pins are connected with the cathode output end of the rectifier bridge;
a pin 1 of an SIC MOSFET module IGBT1 is an anode output end of the second direct current, a pin 2 is a cathode output end of the second direct current and is connected with load equipment to provide power supply of voltage stabilization and constant current; the voltage and current regulation is realized by driving a plurality of SIC MOSFET modules IGBT1 to work in a high-frequency mode, and is specifically realized by outputting a driving signal with pulse width modulation through an RB14 end/RB 15 end of a microcontroller CPU 1.
As shown in fig. 1 and 2, a plurality of MOS transistor isolation control units 100 are connected one-to-one with a plurality of SIC MOSFET modules IGBT 1; namely, each MOS transistor isolation control unit 100 controls one SIC MOSFET module IGBT1 to be suitable for a SIC MOSFET module having only one MOS transistor.
As shown in fig. 3 and 4, the main control unit 300 is connected to a level conversion unit 400, and the main control unit 300 includes: the level conversion circuit comprises a microcontroller CPU1, a first potentiometer VR1 and a second potentiometer VR2, wherein a level conversion unit 400 comprises a plurality of third gate drivers USA1, and the third gate drivers USA1 are respectively connected with the microcontroller CPU1 and an MOS tube isolation control unit 100;
the INA end and the INB end of the third gate driver USA1 are connected with the RB15 end and the RB16 end of the microcontroller CPU1 in a one-to-one mode, and the OUTA end and the OUTB end of the third gate driver USA1 are connected with the MOS tube isolation control unit 100;
the OUTA end of the third gate driver USA1 is connected with the control signal input end of the upper tube MOS transistor isolation control unit 100, and the OUTB end is connected with the control signal input end of the lower tube MOS transistor isolation control unit 100; to control the upper tube MOS transistor isolation control unit 100 and the lower tube MOS transistor isolation control unit 100 in the MOS transistor isolation control unit 100 through the third gate driver USA 1; when the output power is increased, only the SIC MOSFET module IGBT1 (a plurality of SIC MOSFET modules IGBT1 are connected in parallel to increase the output power) and the MOS transistor isolation control unit 100 (to correspondingly control the increased SIC MOSFET module IGBT 1) are added, and the third gate driver USA1 (to correspondingly control the increased MOS transistor isolation control unit 100) is added.
As shown in fig. 1 and 4, the third gate driver USA1 is also connected to a plurality of MOS transistor isolation control units 100; preferably, the third gate driver USA1 is used for controlling the two MOS transistor isolation control units 100, so that the driving capability is strong and stable.
As shown in fig. 3 and 5, the output feedback circuit 500 includes an isolation transmitter S2 and a shunt (not shown) or a voltage dividing resistance unit (not shown); the voltage dividing resistor unit can be two resistors connected in series, the common end of the voltage dividing resistor unit is a voltage dividing output end (a first detection output end), the head end and the tail end of the voltage dividing resistor unit are connected with the positive electrode and the negative electrode of the second direct current one by one, and preferably, one end connected with the negative electrode of the second direct current is a second detection output end;
the Sin-end and the Sin + end of the isolation transmitter S2 are in one-to-one connection with the first detection output end and the second detection output end of the shunt or in one-to-one connection with the first detection output end and the second detection output end of the divider resistance unit;
the Sout + end of the isolation transmitter S2 is connected with the AN2 end or the AN3 end of the microcontroller CPU1, and the Sout-end is grounded;
feedback signal isolation is performed by using an isolation transmitter S2, a shunt is used for detecting the current of the direct current output by the adjusting unit 200, and a divider resistance unit is used for detecting the voltage of the second direct current output by the adjusting unit 200;
further preferably, a shunt is replaced by the Hall direct current sensor, the Hall direct current sensor does not need to be connected with load equipment in series, only the Hall direct current sensor is sleeved on a power supply line, and the installation is easy.
As shown in fig. 2 and 5, the plurality of output feedback circuits 500 includes a current output feedback circuit 500 and a voltage output feedback circuit 500;
the isolation transmitter S2 and the current divider form a current output feedback circuit 500, and the isolation transmitter S2 and the voltage dividing resistance unit form a voltage output feedback circuit 500;
the shunt is connected between the regulating unit 200 and the anode of the load device in series, and the voltage dividing resistance unit is connected to the anode and the cathode of the second direct current in parallel; the circuit is simple, the cost is low, and the volume is small.
As shown in fig. 3, the first input ends of the first potentiometer VR1 and the second potentiometer VR2 are both connected to the positive electrode of the reference power supply, the second input end is connected to the negative electrode of the reference power supply and grounded, the output end of the first potentiometer VR1 is connected to the AN0 end of the microcontroller CPU1, and the output end of the second potentiometer VR2 is connected to the AN1 end of the microcontroller CPU 1; the first potentiometer VR1 is used for adjusting/presetting a regulated voltage value of the second direct current, and the second potentiometer VR2 is used for adjusting/presetting a regulated voltage value of the second direct current.
As shown in fig. 1 and fig. 2, the microcontroller CPU1 supports analog input, and meets the detection requirement of the analog signal input of the output feedback circuit 500; the first gate driving chip U1 is in an isolation type, so that other circuits are isolated from the regulating unit 200/high-power SIC MOSFET module IGBT1, and the stability of the circuit is greatly improved.
It will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are considered to be within the scope of the invention as defined by the following claims.

Claims (10)

1. A power generating power supply controller for an aircraft power generator comprising: the device comprises a main control unit, an isolation control unit and an adjusting unit; the aircraft generator is characterized in that the aircraft generator is connected with a rectifier bridge, the rectifier bridge is connected with the adjusting unit, and the adjusting unit is connected with external load equipment;
the rectifier bridge rectifies alternating current output by the aviation generator into first direct current, and then performs voltage stabilization and constant current output by the adjusting unit to obtain second direct current;
the main control unit is connected with the isolation control unit, and the isolation control unit is connected with the adjusting unit; the main control unit is also connected with a plurality of output feedback circuits, and the output feedback circuits are respectively used for detecting the voltage and the current of the second direct current output by the regulating unit and feeding the voltage and the current back to the main control unit;
the main control unit controls the adjusting unit to regulate voltage/current or not through the isolation control unit according to the voltage and current of the second direct current output by the adjusting unit;
further comprising: and presetting the stabilized voltage value and the constant current value of the second direct current to the main control unit.
2. A power generation controller for an aircraft generator as claimed in claim 1, wherein the isolation control unit comprises: the MOS tube isolation control units are connected with the adjusting unit;
the MOS tube isolation control unit comprises: the MOS transistor isolation control unit comprises a first gate drive chip, AN isolation power module and a second gate drive chip, wherein AN end AN of the first gate drive chip is a control signal input end of the MOS transistor isolation control unit, AN end CAT of the first gate drive chip is grounded, AN end VDD of the first gate drive chip is connected with AN end VO + of the isolation power module, AN end GND of the first gate drive chip is connected with AN end VO-of the isolation power module, AN end VOUT of the first gate drive chip is connected with AN end IN of the second gate drive chip and is also connected with a first resistor, and the other end of the first resistor is connected with AN end V-of the isolation power module;
the VCC1 end and VCC2 end of the second grid drive chip are both connected with the VO + end of the isolation power module, the GND1 end and GND2 end of the second grid drive chip are both connected with the VO-end of the isolation power module, the OUT1 end and OUT2 end of the second grid drive chip are connected and are also connected with a second resistor, the other end of the second resistor is a drive signal output end of the MOS tube isolation control unit, the other end of the second resistor is also connected with a third resistor, and the other end of the third resistor is connected with the GND end of the isolation power module;
the GND end of the isolation power supply module is a driving signal return input end of the MOS tube isolation control unit;
and the driving signal output end and the driving signal return input end of the MOS tube isolation control unit are both connected with the adjusting unit.
3. A power generation controller for an aircraft power generator as claimed in claim 2, wherein a plurality of said MOS transistor isolation control units comprise: the MOS tube isolation control unit is arranged on the upper tube, and the MOS tube isolation control unit is arranged on the lower tube; the adjusting unit comprises a plurality of SIC MOSFET modules, and a plurality of MOS tube isolation control units are connected with the SIC MOSFET modules;
the driving signal output end of the MOS tube isolation control unit of the upper tube is connected with the 4 pins of the SIC MOSFET module, and the driving signal return input end is connected with the 1 pin of the SIC MOSFET module;
the driving signal output end of the MOS tube isolation control unit is connected with the 6 pins of the SIC MOSFET module, and the driving signal return input end is connected with the 2 pins of the SIC MOSFET module;
the 3 pins of the SIC MOSFET module are connected with the positive output end of the rectifier bridge, and the 2 pins of the SIC MOSFET module are connected with the negative output end of the rectifier bridge;
and a pin 1 of the SIC MOSFET module is an anode output end of the second direct current and a pin 2 of the SIC MOSFET module is a cathode output end of the second direct current.
4. The aircraft generator power generation controller as claimed in claim 3, wherein a plurality of said MOS tube isolation control units are connected one-to-one with a plurality of said SIC MOSFET modules.
5. A power generation controller for an aircraft generator as claimed in claim 2, wherein the master control unit is connected to a level shifting unit, the master control unit comprising: the level conversion unit comprises a plurality of third gate drivers, and the third gate drivers are respectively connected with the microcontroller and the MOS tube isolation control unit;
the INA end and the INB end of the third gate driver are connected with the RB15 end and the RB16 end of the microcontroller in a one-to-one mode, and the OUTA end and the OUTB end of the third gate driver are both connected with the MOS tube isolation control unit;
the OUTA end of the third grid driver is connected with the upper tube and the control signal input end of the MOS tube isolation control unit, and the OUTB end of the third grid driver is connected with the lower tube and the control signal input end of the MOS tube isolation control unit.
6. A power generation controller for an aircraft power generator as claimed in claim 5, wherein the third gate driver is further connected to a plurality of said MOS tube isolation control units.
7. The aircraft generator power generation controller of claim 6, wherein the output feedback circuit comprises an isolation transmitter and a shunt or voltage divider resistance unit;
the Sin-end and the Sin + end of the isolation transmitter are in one-to-one connection with the first detection output end and the second detection output end of the shunt or in one-to-one connection with the first detection output end and the second detection output end of the divider resistance unit;
and the Sout + end of the isolation transmitter is connected with the AN2 end or the AN3 end of the microcontroller, and the Sout-end is grounded.
8. A power generation supply controller for an aircraft power generator as claimed in claim 7, wherein a plurality of said output feedback circuits includes a current said output feedback circuit and a voltage said output feedback circuit;
the isolation transmitter and the current divider form the current output feedback circuit, and the isolation transmitter and the voltage dividing resistance unit form the voltage output feedback circuit;
the shunt is connected between the regulating unit and the anode of the load device in series, and the voltage dividing resistance unit is connected to the anode and the cathode of the second direct current in parallel.
9. The aircraft generator power generation controller as claimed in claim 5, wherein the first input ends of the first potentiometer and the second potentiometer are connected with the positive pole of a reference power supply and the second input ends are connected with the negative pole of the reference power supply and grounded, the output end of the first potentiometer is connected with the AN0 end of the microcontroller, and the output end of the second potentiometer is connected with the AN1 end of the microcontroller.
10. The aircraft generator power-generating controller of claim 5, wherein the microcontroller supports an analog input; the first grid driving chip is of an isolation type.
CN202223062293.5U 2022-11-18 2022-11-18 Power generation power supply controller of aero-generator Active CN218630564U (en)

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Application Number Priority Date Filing Date Title
CN202223062293.5U CN218630564U (en) 2022-11-18 2022-11-18 Power generation power supply controller of aero-generator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202223062293.5U CN218630564U (en) 2022-11-18 2022-11-18 Power generation power supply controller of aero-generator

Publications (1)

Publication Number Publication Date
CN218630564U true CN218630564U (en) 2023-03-14

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